Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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(naca64210-il) NACA 64-210 | NACA 64-210 airfoil Max thickness 10% at 40% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(bacnlf-il) BOEING HSNLF AIRFOIL | Boeing high speed natural laminar flow airfoil from a European patent (EP 0111785A1) Max thickness 10.1% at 43.7% chord Max camber 1.3% at 76.7% chord | Remove Airfoil details Airfoil plotter |
(e559-il) EPPLER 559 AIRFOIL | Eppler E559 general aviation airfoil Max thickness 16% at 27.2% chord Max camber 4.3% at 50.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca64210-il,bacnlf-il,e559-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca64210-il | 50,000 | 9 | 30.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64210-il | 50,000 | 5 | 32.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64210-il | 100,000 | 9 | 46.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64210-il | 100,000 | 5 | 44.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64210-il | 200,000 | 9 | 61.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64210-il | 200,000 | 5 | 54 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64210-il | 500,000 | 9 | 76.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64210-il | 500,000 | 5 | 63.2 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64210-il | 1,000,000 | 9 | 85.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64210-il | 1,000,000 | 5 | 72.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacnlf-il | 50,000 | 9 | 26.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacnlf-il | 50,000 | 5 | 28.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacnlf-il | 100,000 | 9 | 35.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacnlf-il | 100,000 | 5 | 40.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacnlf-il | 200,000 | 9 | 55.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacnlf-il | 200,000 | 5 | 53 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacnlf-il | 500,000 | 9 | 78.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacnlf-il | 500,000 | 5 | 64.9 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacnlf-il | 1,000,000 | 9 | 88.3 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacnlf-il | 1,000,000 | 5 | 66.1 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e559-il | 50,000 | 9 | 8.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e559-il | 50,000 | 5 | 30.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e559-il | 100,000 | 9 | 43.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e559-il | 100,000 | 5 | 52.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e559-il | 200,000 | 9 | 70.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e559-il | 200,000 | 5 | 73.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e559-il | 500,000 | 9 | 103.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e559-il | 500,000 | 5 | 101.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e559-il | 1,000,000 | 9 | 130.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e559-il | 1,000,000 | 5 | 123.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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